Classifications

• • C—CHEMISTRY; METALLURGY
  • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
  • C22C—ALLOYS
  • C22C21/00—Alloys based on aluminium
  • C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
• • C—CHEMISTRY; METALLURGY
  • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
  • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
  • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
  • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
  • C22F1/047—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with magnesium as the next major constituent

Definitions

• ALUMINUM ALLOY PRODUCT This invention relates to an aluminum alloy product, and more particularly to aluminum alloy products developed for aerospace applications. Nearly all commercial airplanes have fuselage skins made of Alclad 2024-T3.
• the base metal, 2024-T3 sheet has the necessary strength and damage tolerance for aerospace applications, but suffers from susceptibility to pitting and/or intergranular corrosion attack. To compensate for that problem, the base metal is effectively isolated from the environment by a cladding layer, a paint or coating system or a combination of both.
• An alcladding process involves combining a thin layer of an aluminum alloy anodic relative to
• 2024-T3 on both sides of 2024-T3 sheet. These layers act as a barrier and also afford galvanic protection to the 2024-T3 in case the cladding is damaged. In cases where these layers are intentionally removed by machining or chemical milling to save weight, 2024-T3 sheet may be protected with coatings and/or by anodization.
• the Alclad layer contributes little with respect to strength, adds weight to the sheet and can act to initiate fatigue cracks.
• Other coating systems may also add weight and, if damaged, fail to protect 2024-T3 base metal. Surfaces that are anodized are brittle and can act to initiate cracks.
• Another disadvantage of 2024-T3 sheet is its relatively high density (0.101 lb/in 3 ) .
• the alloys of this invention have a relatively low density, good corrosion resistance and a good combination of strength and toughness so as to obviate cladding, painting and/or other base metal protection systems.
• One embodiment of the present invention pertains to an aluminum alloy product comprising an alloy composition which includes about 3-7 wt % magnesium, about 0.03-0.20 wt % zirconium, about 0.2- 1.2 wt % manganese, up to 0.15 wt % silicon and about 0.05-0.5 wt % of a dispersoid- forming element selected from the group consisting of: scandium, erbium, yttrium, gadolinium, holmium and hafnium, the balance being aluminum and incidental elements and impurities. It is preferred that the dispersoid-forming element is scandium.
• This alloy composition is also preferably zinc- free and lithium- free.
• substantially free means having no significant amount of that component purposely added to the alloy composition, it being understood that trace amounts of incidental elements and/or impurities may find their way into a desired end product.
• the alloys of the invention are based on the Al-Mg-Sc system and are of sufficient corrosion resistance so as to obviate cladding or other protection systems. Strength in these alloys is primarily generated through, strain hardening of a metal matrix which is generally uniform in composition. Combinations of strength and damage tolerance properties sufficient for fuselage skin applications can be obtained by an appropriate selection of composition, deformation processing and subsequent stabilization treatments.
• Al-Mg-Sc alloy materials of this invention display adequate tensile strength properties and toughness indicators together with excellent resistance to intergranular (or grain boundary) corrosion. These materials, also demonstrate good resistance to exfoliation attack and excellent stress corrosion cracking ("SCC") resistance during alternate immersion in an NaCl solution tested according to ASTM G-47.
• SCC stress corrosion cracking
• a principal alloy embodiment of this invention comprises an alloy composition which includes about 3-7 wt % magnesium, about 0.03-0.2 wt % zirconium, about 0.2-1.2 wt % manganese, up to 0.15 wt % silicon, and about 0.05-0.5 wt % of a dispersoid- forming element selected from the group consisting of: scandium, erbium, yttrium, gadolinium, holmium and hafnium, the balance being aluminum and incidental elements and impurities.
• the aluminum alloy composition contains about 3.5-6 wt % magnesium; about 0.06-0.12 wt % zirconium; about 0.4-1 wt % manganese, up to 0.08 wt % silicon and about 0.16-0.34 wt % scandium.
• the aluminum alloy composition consists essentially of about 3.8-5.2 wt % magnesium; about 0.09-0.12 wt % zirconium, about 0.5-0.7 wt % manganese, up to 0.05 wt % silicon and about 0.2-0.3 wt % scandium.
• Preferred embodiments of this aluminum alloy are also substantially zinc- free and lithium-free.
• this invention manages to impart significantly higher strengths and greater corrosion resistance to fuselage skin sheet stock through the addition of certain rare earths or rare earth "act-alikes" , such as scandium, by causing rare earth-rich precipitates to form. These precipitates have the ability to store and resist loss of strength arising from plastic deformation. Because of the relatively small size and fine distribution of these particles, recovery and recrystallization of the resulting alloy are also inhibited.
• the invention alloy is more temperature resistant than the same alloy devoid of scandium or scandium-like additives.
• temperature resistant it is meant that a large portion of the strength and structure imparted by working this alloy is retained in the fuselage skin sheet end product, even after exposure to one or more higher temperatures, typically above about 450°F., such as during subsequent rolling operations or the like.
• a remainder of substantially aluminum may include some incidental, yet intentionally added elements which may affect collateral properties of the invention, or unintentionally added impurities, neither of which should change the essential characteristics of this alloy.
• magnesium contributes to strain hardening and strength. Zirconium additions are believed to improve the resistance of scandium precipitates to rapid growth.
• Scandium and zirconium serve yet another purpose.
• scandium is believed to precipitate to form a dispersion of fine, intermetallic particles (referred to as "dispersoids") , typically of an A1 3 X stoichio etry, with X being either Sc, Zr or both Sc and Zr.
• Al 3 (Sc, Zr) dispersoids impart some strength benefit as a precipitation-hardening compound, but more importantly, such dispersoids efficiently retard or impede the process of recovery and recrystallization by a phenomenon sometimes called the "Zener Drag" effect. [See generally, C.S.
• Scandium dispersoids are very small in size, but also large in number. They generally act as “pinning” points for migrating grain boundaries and dislocations which must bypass them for metal to soften. Recrystallization and recovery are the principal metallurgical processes by which such strain hardenable alloys soften. In order to "soften” an alloy having a large population of Al 3 (Sc, Zr) particles, it is necessary to heat the material to higher temperatures than would be required for an alloy not having such particles.
• a sheet product that contains Al 3 (Sc, Zr) dispersoids will have higher strength levels than a comparable alloy to which no scandium was added.
• this invention exhibits an ability to resist softening during the high temperature thermal exposures usually needed to roll sheet products. In so doing, the invention alloy will retain some of the strength acquired through rolling. Other scandium-free alloys would tend to retain less strength through rolling, thus yielding a lower strength final product.
• An added benefit of zirconium is its ability to limit the growth of these A1 3 X particles to assure that such dispersoids remain small, closely spaced and capable of producing a Zener Drag effect.
• the alloy of this invention may contain up to 0.15 wt % silicon with up to 0.08 wt % being preferred and 0.05 wt % or less being most preferred.
• the alloy products described herein may accommodate up to about 0.25 wt % copper or preferably about 0.15 wt % Cu or less.
• the aluminum alloy product of this invention is especially suited for applications where damage tolerance is required.
• damage tolerant aluminum products are used for aerospace applications, particularly fuselage skin, and the lower wing sections, stringers or pressure bulkheads of many airplanes.
• each alloy being aluminum, incidental elements and impurities.
• All of the aforementioned alloys were direct chill (or "DC") cast as 2-1/2 x 12 inch ingots and the rolling surfaces scalped therefrom. Alloy A was not homogenized. Alloy B was homogenized for 5 hours at 550°F. followed by 5 hours at 800°F. Alloy C was homogenized for 5 hours at 500°F., then for 6 more hours at 750°F. The scalped ingots were heated to 550°F. for 30 minutes and cross rolled approximately 50% to a nominal thickness of 1 inch. Alloys A and B were then reheated to 550°F. and rolled to a final nominal thickness of 0.1 inch. Mechanical properties for each alloy were then evaluated after a stabilization treatment of 5 hours at 550°F.
• Alloy C was heated to 700°F. and cross rolled to approximately 1 inch thick. This slab was then reheated to 530°F. and rolled to 0.5 inch thickness. The resulting plate from Alloy C was then aged for 15 hours at 500°F. until the electrical conductivity increased to 28.0% of the International Annealed Copper Standard (or "IACS"). Alloy C plate was then heated again to 500°F. and warm rolled to a final thickness of 0.1 inch before being subjected to its final heat treatment of 2 hours at 500°F.
• IACS International Annealed Copper Standard
• Table I reports the physical, mechanical property and corrosion data available for the foregoing samples of Alloys A, B and C, then compares them with typical values for 2024-T3 aluminum, 6013-T6 aluminum and another potential fuselage skin material known commercially as Alcoa's C-188 product as manufactured in accordance with U.S. Patent No. 5,213,639, the full disclosure of which is expressly incorporated herein by reference.
• the materials of this invention display adequate tensile strength properties.
• the toughness indicators of Alloy A and B, per center notch toughness and fatigue crack growth (or "FCG") data also strongly indicate that these materials will exhibit good inherent toughnesses as well.
• the resistance to grain boundary corrosion attack of the present invention is also noteworthy.
• a standard test for measuring such attacks in Al-Mg base alloys is the ASSET (or ASTM G- 66) test after a "sensitization" treatment at 212°F.
• the subject materials demonstrated good resistance to exfoliation attack in that test with only Alloy B showing any evidence of exfoliation, and even then to just an EA level. By comparison, other materials showed some pitting attack (P) with minimal blistering.
• the invention materials also showed excellent SCC resistance during alternate immersion testing using an NaCl solution.

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• Physics & Mathematics (AREA)
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• Crystallography & Structural Chemistry (AREA)
• Manufacture Of Alloys Or Alloy Compounds (AREA)
• Other Surface Treatments For Metallic Materials (AREA)
• Powder Metallurgy (AREA)

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• 1997
  • 1997-02-10 JP JP53428098A patent/JP4014229B2/ja not_active Expired - Fee Related
  • 1997-02-10 CA CA002280191A patent/CA2280191C/en not_active Expired - Fee Related
  • 1997-02-10 ES ES97906549T patent/ES2188897T3/es not_active Expired - Lifetime
  • 1997-02-10 DE DE69717858T patent/DE69717858T2/de not_active Revoked
  • 1997-02-10 AU AU21211/97A patent/AU2121197A/en not_active Abandoned
  • 1997-02-10 WO PCT/US1997/002117 patent/WO1998035068A1/en not_active Application Discontinuation
  • 1997-02-10 KR KR10-1999-7007143A patent/KR100469929B1/ko not_active IP Right Cessation
  • 1997-02-10 EP EP97906549A patent/EP0958393B1/de not_active Revoked

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